Afterbody/nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2
By: David J. Wing.
Contributors: Langley Research Center.
Series: NASA technical paper -- 3509.
Publisher: National Aeronautics and Space Administration, Langley Research Center; Available from the National Technical Information Service
Published: 1995
Place of publication: Hampton, Va; Springfield, VA
Language: eng
Number of pages: 209
Subjects: Aerodynamic load; Jet nozzles
Other titles: Afterbody nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2.
Notes: "May 1995."

"Performing organization report number L-17438"--Report documentation page.

Includes bibliographical references (p. 10).

Available electronically at the following URL address: http://techreports.larc.nasa.gov/ltrs/ltrs.html.

WU 505-59-30-04.